This paper reports on work completed to develop an analytical method for predicting the transient nonlinear response of a complete aircraft engine system due to the loss of a fan blade, and to validate the analysis by comparing the results against actual blade loss test data. The solution, which is based on the component element method, accounts for rotor-to-casing rubs, high damping, and rapid deceleration rates associated with the blade loss event. A comparison of test results and predicted response show good agreement except for an initial overshoot spike not observed in test. The method is effective for analysis of large systems.


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    Titel :

    Blade loss transient dynamic analysis of turbomachinery


    Weitere Titelangaben:

    Analyse des Schwingungsverhaltens von Flugzeugturbinen bei Schaufelverlust


    Beteiligte:
    Stallone, M.J. (Autor:in) / Gallardo, V. (Autor:in) / Storace, A.F. (Autor:in) / Bach, L.J. (Autor:in) / Black, G. (Autor:in) / Gaffney, E.F. (Autor:in)

    Erschienen in:

    AIAA Journal ; 21 , 8 ; 1134-1138


    Erscheinungsdatum :

    1983


    Format / Umfang :

    5 Seiten, 13 Bilder, 1 Tabelle, 8 Quellen



    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




    Blade loss transient dynamic analysis of turbomachinery

    Stallone, M. J. / Gallardo, V. / Storace, A. F. et al. | NTRS | 1983


    Blade loss transient dynamic analysis of turbomachinery

    STALLONE, M. / GALLARDO, V. / STORACE, A. et al. | AIAA | 1982


    Blade loss transient dynamic analysis of turbomachinery

    STALLONE, M. J. / GALLARDO, V. / STORACE, A. F. et al. | AIAA | 1983


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